CN208868281U - Unmanned plane damping fuselage - Google Patents
Unmanned plane damping fuselage Download PDFInfo
- Publication number
- CN208868281U CN208868281U CN201821214624.3U CN201821214624U CN208868281U CN 208868281 U CN208868281 U CN 208868281U CN 201821214624 U CN201821214624 U CN 201821214624U CN 208868281 U CN208868281 U CN 208868281U
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- China
- Prior art keywords
- damping
- bulkhead
- fuselage
- unmanned plane
- block
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Abstract
A kind of unmanned plane damping fuselage comprising fuselage cover and damping bulkhead, the damping bulkhead is interior loaded on fuselage cover and fills fuselage shell inner cavity, forms the damping airframe structure of unmanned plane；The damping bulkhead is foam bulkhead or hardhead sponge bulkhead, offers component mounting groove on the damping bulkhead, radiator structure and Wiring structure is additionally provided in the damping bulkhead, the radiator structure is connected to mounting groove with Wiring structure.Fuselage cover is built-in with a damping bulkhead for being able to cooperate installation electrical component, the damping bulkhead is foam bulkhead resistant to high temperature or hardhead sponge bulkhead, to effectively promote damping effect of the unmanned aerial vehicle body in descent, to further promote the cushioning ability of entire unmanned plane.
Description
Technical field
The utility model relates to unmanned plane fields, shake when can reduce landing more particularly, to one kind and give unmanned plane electronics
The unmanned plane damping fuselage of element bring damage.
Background technique
With the development of unmanned plane manufacturing technology, unmanned plane using more and more extensive, the in-flight problem therewith
Also more and more, especially: when unmanned slide landing, since sinking speed is fast, landing process generates vibration, the vibration
Different degrees of damage is caused for unmanned plane and its electronic component being attached on unmanned plane body；In addition, because pacifying on unmanned plane
A variety of electronic components are filled, and number of electronic components is larger, caused all more miscellaneous in the connection of existing unmanned aerial vehicle body internal wiring
Disorderly, not only viewing comes unsightly outside, but also will often find that the case where electronic component is interfered in route knotting.
Summary of the invention
The utility model solves the problems, such as it is how to effectively increase unmanned aerial vehicle body damping effect, to reduce vibration to nothing
It is damaged caused by the damage of man-machine interior electronic component, and reinforcement of the damping bulkhead to fuselage framework.
To solve the above problems, the utility model provides a kind of technical solution of unmanned plane damping fuselage comprising fuselage
Shell and damping bulkhead, the damping bulkhead is interior loaded on fuselage cover and fills fuselage shell inner cavity, forms the damping of unmanned plane
Airframe structure；
The damping bulkhead is foam bulkhead or hardhead sponge bulkhead, offers component mounting groove on the damping bulkhead, this subtracts
It is additionally provided with radiator structure and Wiring structure in shake bulkhead, the radiator structure is connected to mounting groove with Wiring structure.
Further preferred that the radiator structure is heat release hole or/and radiating groove.
Further preferred that the Wiring structure is cable hole or/and cabling channel.
Further preferred that the damping bulkhead is foam bulkhead or hardhead sponge bulkhead.
Further preferred that the damping bulkhead is successively clamped or is bonded shape along fuselage cover direction by multiple bulkhead blocks
At.
Further preferred that the multiple bulkhead block is respectively battery containing block, the camera being sequentially placed into fuselage cover
Pedestal accommodates block and flight control surface plate accommodates block.
Further preferred that battery settling groove is offered on the battery containing block, and the bottom surface of battery settling groove is rank
Tread, the bottom surface of the battery containing block offers can be with the cabling channel of power supply, phase mechatronics.
Further preferred that offering cylindric mounting groove on the camera pedestal accommodating block.
Further preferred that offering the winged control plate peace that a cooperation flies control plate installation on the flight control surface plate accommodating block
Tankage.
Compared with prior art, the utility model has the advantage that
The utility model is built-in with a damping bulkhead for being able to cooperate installation electrical component, the damping bulkhead in fuselage cover
For foam bulkhead resistant to high temperature or hardhead sponge bulkhead, so that damping effect of the unmanned aerial vehicle body in descent is effectively promoted,
To further promote the cushioning ability of entire unmanned plane；In addition, also opening up radiator structure on damping bulkhead in this programme and walking
Cable architecture is also able to achieve effective heat dissipation while promoting damping effect to realize, to promote the heat dissipation effect of entire fuselage
Fruit, thus the service life of lift fuselage, and the conducting wire by electrical component each in fuselage of the setting auxiliary of Wiring structure is orderly
Arrangement promotes the cleaning and aesthetics of entire fuselage electrical component distribution.
Detailed description of the invention
Fig. 1 is the utility model embodiment structural decomposition diagram；
Fig. 2 is damping bulkhead and power panel platform assembling structure stereoscopic schematic diagram in the utility model embodiment；
Fig. 3 is damping bulkhead and power panel platform assembling structure main view in the utility model embodiment；
Fig. 4 is damping bulkhead and power panel platform assembling structure top view in the utility model embodiment；
Fig. 5 is damping bulkhead and power panel platform assembling structure bottom view in the utility model embodiment.
Specific embodiment
When unmanned slide landing, since sinking speed is fast, generate vibration when landing, the vibration for unmanned plane and
Its electronic component being attached on unmanned plane body causes different degrees of damage；In addition, because installing a variety of electronics members on unmanned plane
Part, and number of electronic components is larger, causes in the connection of existing unmanned aerial vehicle body internal wiring all more in a jumble, not only in appearance
Apparently unsightly, the case where and will often find that route knotting interference electronic component.
In view of the above technical problems, by the analysis to reason, constantly research finds a kind of unmanned plane damping machine to inventor
The technical solution of body comprising fuselage cover and damping bulkhead, the damping bulkhead is interior loaded on fuselage cover and fills outside fuselage
Shell inner cavity forms the damping airframe structure of unmanned plane；Component mounting groove is offered on the damping bulkhead, in the damping bulkhead also
It is provided with radiator structure and Wiring structure, the radiator structure is connected to mounting groove respectively with Wiring structure.
In above-mentioned technical proposal, it is built-in with a damping bulkhead for being able to cooperate installation electrical component in fuselage cover, it is described to subtract
Shaking bulkhead is foam bulkhead resistant to high temperature or hardhead sponge bulkhead, to effectively promote damping of the unmanned aerial vehicle body in descent
Effect, to further promote the cushioning ability of entire unmanned plane；In addition, also opening up radiator structure on damping bulkhead in this programme
And Wiring structure, it is also able to achieve effective heat dissipation while promoting damping effect to realize, to promote dissipating for entire fuselage
Thermal effect, thus the service life of lift fuselage, and the conducting wire by electrical component each in fuselage of the setting auxiliary of Wiring structure
Ordered arrangement promotes the cleaning and aesthetics of entire fuselage electrical component distribution.
Specific embodiment of the present utility model is described in detail with reference to the accompanying drawing.
Embodiment:
As shown in Figure 1 to Figure 2, a kind of technical solution of unmanned plane damping fuselage comprising fuselage cover 1 and damping bulkhead
2, the damping bulkhead 2 is interior loaded on fuselage cover 1 and fills fuselage shell inner cavity, forms the damping airframe structure of unmanned plane.
As shown in Figure 1, the fuselage cover 1 is made of selection carbon fibre material, to have light weight, intensity is big and energy
Effectively ensure fuselage stabilization and service life.
As shown in Figure 1, the damping bulkhead 2 be can by multiple electronic components it is orderly and stable be installed on fuselage cover 1
Interior fixed frame, the damping bulkhead 2 are foam bulkhead or hardhead sponge bulkhead, and component peace is offered on the damping bulkhead 2
Tankage, is additionally provided with radiator structure and Wiring structure in the damping bulkhead 2, and the radiator structure and Wiring structure are and mounting groove
Connection.Specifically: the damping bulkhead 2 can be formed by mold or be formed through three dimensional sculpture.
Specifically: as shown in Figures 3 to 5, the radiator structure is heat release hole or/and radiating groove, the Wiring structure
Selection for cable hole or/and cabling channel, the heat release hole or/and radiating groove opens up, and is determined according to specific actual conditions
Fixed, the heat release hole is through-hole, and radiating groove is then the groove for being able to achieve air flowing to realize heat dissipation, in addition, the cabling
The selection of hole or/and cabling channel opens up, and is to be determined according to specific practical cabling situation, uses cabling channel under normal circumstances,
And cabling channel is the groove of energy buried line.
As shown in Figures 2 to 5, the damping bulkhead 2, which can be integrally formed, is also possible to by multiple bulkhead blocks along fuselage
Shell direction is successively clamped or is bonded formation, integrally formed to be more troublesome in operation, because multiple bulkhead blocks are placed on
In fuselage cover 1, have many advantages, such as to facilitate operation and installation, and then from actual processing convenience and processing cost by damping
Bulkhead 2 becomes more designer using the structure of multiple bulkhead blocks, production and processing producer is favored.
As shown in Figures 2 to 5, the damping bulkhead 2 is successively clamped or is bonded along fuselage cover direction by multiple bulkhead blocks
It is formed.Specifically: it can be connected with each other by the buckle of mechanical structure between the adjacent formers block, it can also be in bonding plane
Gluing is to realize that the mutual year between bulkhead block is connected, and in practical operation, manufacturing procedure and cost consideration, in adjacent bulkhead
Mucigel cooperation is formed by gluing between block to be connected as preferred connection type and connection structure.
In the present embodiment:
As shown in Figures 2 to 5, the damping bulkhead 2 is successively bonded along fuselage cover direction by three bulkhead blocks and is formed, institute
The docking side for stating adjacent formers block carries out bonding by mucigel and is connected；Specifically: three bulkhead blocks be respectively according to
The secondary battery containing block 21 being placed in fuselage cover, camera pedestal accommodating block 22 and flight control surface plate accommodate block 23.
In more detail: as shown in Figures 2 to 5, battery settling groove 211 is offered on the battery containing block 21, and it is electric
The bottom surface of pond mounting groove 211 is cascaded surface, and the bottom surface of the battery containing block 21 offers can be with the cabling of power supply, phase mechatronics
Slot, in offering 10 heat release holes 212 on the bottom surface of battery settling groove and each heat release hole is opened in 211 bottom surface of battery settling groove
On, each heat release hole 212 be rectangular opening and its be through-hole, 10 heat release holes 212 incline arranges in two column, five row matrix, each heat release hole
212 are obliquely installed, and two column heat release holes 212 are symmetrical arranged, wherein the through-hole close to camera pedestal accommodating 22 side of block is to walk
String holes 213 and its be connected to a perforation cabling channel 3, the cable hole 213 is two and is respectively placed in ten 212 holes two of heat dissipation
Side, 21 side of battery containing block offer a wire casing 214 for being coupled antenna, can install antenna and antenna at the wire casing
Shell can be passed through and stretch out in shell；Cylindric mounting groove 221, cylindrical shape peace are offered on the camera pedestal accommodating block 22
221 side of tankage offers a cable hole 222, which is through-hole and rounded, and perforation described in the cable hole 222 is walked
Wire casing 3 is connected to；The winged control plate mounting groove 231 that a cooperation flies control plate installation, institute are offered on the flight control surface plate accommodating block
State that fly control plate mounting groove 231 be rectangle shallow slot, and in offering 12 heat release holes 232 on the bottom surface of battery settling groove 231, it is each to dissipate
Hot hole 232 be rectangular opening and its be through-hole, 12 heat release holes 232 incline arranges in two column, six row matrix, and each inclination of heat release hole 232 is set
Set, and two column heat release holes 232 be symmetrical arranged, wherein far from camera pedestal accommodating 22 side of block a through-hole be cable hole and its with
One perforation cabling channel 3 is connected to.
As shown in Figures 2 to 5, above-mentioned perforation cabling channel 3 is a groove for being opened in damping bulkhead bottom surface edge, this is passed through
Logical cabling channel 3 is by three bulkhead block bondings and perforation is connected, and the cable hole for being opened in camera pedestal accommodating block 22, which is opened in, to be passed through
In logical cabling channel.To form the Wiring structure that perforation connects multiple electronic components, formation effectively can radiate and be mutually communicated
Wiring structure.
As shown in Figures 2 to 5, three above-mentioned frame blocks are half block structure, and the mounting groove opened up thereon is capable of fixing pair
The electrical component answered, each frame block are loaded on fuselage cover lower half, further realize fuselage damping if wanting to reach, can will remain
The remaining half cavity filled and process block or hard foam block full for filling, fuselage cover can be filled full damping knot by forming one
Structure.The rear of three frame blocks is additionally provided with a power panel platform 4, which is a plate and opens up thereon
There are cable hole and heat release hole, which can be overlapped in flight control surface plate accommodating block edge.
Although the utility model is disclosed as above with preferred embodiment, its be not for limiting the utility model, it is any
Those skilled in the art without departing from the spirit and scope of the utility model, can make possible variation and modification, because
This protection scope of the utility model should be subject to the range that the utility model claims are defined.
Claims (8)
1. unmanned plane damping fuselage, it is characterised in that: it includes fuselage cover and damping bulkhead, and the damping bulkhead is loaded on fuselage
In shell and fuselage shell inner cavity is filled, forms the damping airframe structure of unmanned plane；
The damping bulkhead is foam bulkhead resistant to high temperature or hardhead sponge bulkhead, offers component mounting groove on the damping bulkhead,
Radiator structure and Wiring structure are additionally provided in the damping bulkhead, the radiator structure is connected to mounting groove with Wiring structure.
2. unmanned plane damping fuselage according to claim 1, it is characterised in that: the radiator structure be heat release hole or/and
Radiating groove.
3. unmanned plane damping fuselage according to claim 1, it is characterised in that: the Wiring structure be cable hole or/and
Cabling channel.
4. unmanned plane damping fuselage according to claim 1, it is characterised in that: the damping bulkhead is by multiple bulkhead blocks edge
Fuselage cover direction is successively clamped or is bonded formation.
5. unmanned plane damping fuselage according to claim 4, it is characterised in that: the multiple bulkhead block is respectively successively set
Block is accommodated in battery containing block, camera pedestal accommodating block and the flight control surface plate in fuselage cover.
6. unmanned plane damping fuselage according to claim 5, it is characterised in that: offer battery on the battery containing block
Mounting groove, and the bottom surface of battery settling groove is cascaded surface, the bottom surface of the battery containing block offers can be with power supply, phase mechatronics
Cabling channel.
7. unmanned plane damping fuselage according to claim 5, it is characterised in that: offered on the camera pedestal accommodating block
Cylindric mounting groove.
8. unmanned plane damping fuselage according to claim 5, it is characterised in that: opened on the flight control surface plate accommodating block
Fly the winged control plate mounting groove of control plate installation equipped with a cooperation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821214624.3U CN208868281U (en) | 2018-07-30 | 2018-07-30 | Unmanned plane damping fuselage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821214624.3U CN208868281U (en) | 2018-07-30 | 2018-07-30 | Unmanned plane damping fuselage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208868281U true CN208868281U (en) | 2019-05-17 |
Family
ID=66463668
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821214624.3U Active CN208868281U (en) | 2018-07-30 | 2018-07-30 | Unmanned plane damping fuselage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208868281U (en) |
-
2018
- 2018-07-30 CN CN201821214624.3U patent/CN208868281U/en active Active
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